Gas turbine blade, manufacturing method therefor, and gas turbine using turbine blade

ABSTRACT

Gas turbine blades which simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. Cooling channels provided in the interior of a gas turbine blade include a plurality of straight channel-like base-side elongated holes extending in a longitudinal direction at a base side of the turbine blade, a plurality of straight channel-like tip-side elongated holes extending in a longitudinal direction at a tip side of the turbine blade, and a plurality of communicating hollow portions interposed at connection portions between the two types of elongated holes to allow the two types of elongated holes to communicate with each other, and have larger cross-sectional areas than the channel cross-sectional areas of both elongated holes. The communicating hollow portions are formed to match the position of a platform portion of the turbine blade.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of U.S. application Ser. No.12/960,970, filed Dec. 6, 2010, which is hereby incorporated byreference herein in its entirety.

This application is based on Japanese Patent Application No.2010-046687, which is hereby incorporated by reference herein in itsentirety.

TECHNICAL FIELD

The present invention relates to gas turbine blades used in thermalpower generation and so forth and relates, more specifically, to gasturbine blades in which cooling channels formed inside the turbineblades are improved, to a manufacturing method therefor, and to a gasturbine using the turbine blades.

BACKGROUND ART

In a gas turbine, because high-temperature working fluid flows in thearea surrounding turbine blades, in general, cooling channels are formedinside the turbine blades in the longitudinal direction of the turbineblades, and cooling of the turbine blades is performed by streamingcooling air through the cooling channels. Part of the air compressed bya turbine compressor is extracted and fed into the cooling channels asthe cooling air, and this cooling air flows through the cooling channelsto cool the turbine blades from inside, thereby protecting the turbineblades from the heat of the high-temperature working fluid (combustiongas). Known conventional gas turbines (gas turbine blades) employingsuch a configuration include technology disclosed in Patent Literature1.

In the conventional gas turbine disclosed in Patent Literature 1, asingle-space hollow portion is formed from a base side of a turbineblade toward a tip side thereof, whereas a plurality ofstraight-channel-like elongated holes are formed from the tip side ofthe turbine blade toward the base side thereof; and these elongatedholes communicate with the hollow portion at a mid portion of theturbine blade in the longitudinal direction. In addition, the hollowportion is widened at the portion communicating with the elongatedholes. Accordingly, when forming the elongated holes from the tip sideof the turbine blade by machining, the elongated holes are readily madeto communicate with the hollow portion, and machining thereof is easy.

CITATION LIST Patent Literature

-   {PTL 1} Japanese Unexamined Patent Application, Publication No.    2007-211618.

SUMMARY OF INVENTION Technical Problem

However, with the structure in Patent Literature 1, because the hollowportion is formed as a single space, the effective cross-sectional areaof the turbine blade ends up being reduced at this portion, thus causinga loss of turbine blade strength and rigidity; in the worst case,breakage (creep rupture, etc.) may be caused, and there has been a lackof reliability. On the other hand, if no hollow portion is provided buta plurality of straight-channel-like forms are formed by applyingelongated-hole machining from both sides of the tip side and the baseside of the turbine blade and connecting the channel-like forms at a midportion so as to form one elongated hole, the effective cross-sectionalarea of the turbine blade can be increased for the space made byproviding no hollow portion. However, in this method, it is difficult toalign centers of the channel-like forms at the time of elongated-holemachining from two opposite directions, which may increase the machiningcosts or decrease the production yield due to incomplete penetration ofthe elongated holes with each other.

The present invention has been conceived in light of the above-describedcircumstances, and an object thereof is to provide gas turbine bladesthat are capable of simplifying the formation of cooling channelsprovided inside the turbine blades while simultaneously being capable ofavoiding a loss of turbine blade strength and rigidity due to theformation of the cooling channels, thus being highly reliable, as wellas to provide a manufacturing method therefor and a gas turbineemploying the turbine blades.

Solution to Problem

In order to solve the above-described problems, the present inventionemploys the following solutions.

Specifically, gas turbine blades according to a first aspect of thepresent invention are gas turbine blades in which cooling channels areformed inside the turbine blades, and the turbine blades are cooled bycausing cooling air to circulate through the cooling channels, whereinthe cooling channels include a plurality of straight channel-likebase-side elongated holes that extend in a longitudinal direction at abase side of the turbine blade, a plurality of straight channel-liketip-side elongated holes that extend in a longitudinal direction at atip side of the turbine blade, and a plurality of communicating hollowportions that are interposed at connection portions between thebase-side elongated holes and the tip-side elongated holes toindividually allow the two types of elongated holes to communicate witheach other and that have larger cross-sectional areas than the channelcross-sectional areas of the two types of elongated holes.

According to the present invention, for example, when forming thetip-side elongated holes from the tip side of the turbine blades afterforming the base-side elongated holes and the communicating hollowportions, because cross-sectional areas of the communicating hollowportions are larger than channel cross-sectional areas of the base-sideelongated holes and the tip-side elongated holes, the tip-side elongatedholes can easily penetrate the communicating hollow portions.Accordingly, it is possible to simplify the formation of the coolingchannels formed inside the turbine blades. In addition, because thebase-side elongated holes are formed in the plurality ofstraight-channel-like forms instead of a single hollow portion, it ispossible to avoid the loss of turbine blade strength and rigidity causedby the formation of the cooling channels.

In addition, in gas turbine blades according to a second aspect of thepresent invention, the communicating hollow portions are formed so as tomatch the position of the platform portion of the turbine blade.Accordingly, the communicating hollow portions having the largestlateral cross-sectional areas among the cooling channels are formedinside the platform portions where the plate thickness is the largest inthe turbine blades; therefore, portions where the effectivecross-sectional areas of the turbine blades become small in practice areminimized, and thus, it is possible to prevent the loss of turbine bladestrength and rigidity.

Furthermore, in gas turbine blades according to a third aspect of thepresent invention, among the plurality of the communicating hollowportions, the communicating hollow portions that are adjacent to eachother are set at different heights. Accordingly, the communicatinghollow portions adjacent to each other are prevented from being arrangedat the same height, thereby increasing the distance between theindividual communicating hollow portions; therefore, the effectivecross-sectional areas of the turbine blades are prevented from beingreduced at the positions of the communicating hollow portions, therebymaking it possible to prevent the loss of turbine blade strength andrigidity.

Furthermore, in gas turbine blades of the present invention, at leastlengths from tip ends of the plurality of the tip-side elongated holesto the communicating hollow portions are set to be the same.Accordingly, simultaneous machining with a plurality of electrodes ordrills is possible, variance in the accuracy of machining of theelongated holes does not occur, and the accuracy of machining is muchimproved.

Additionally, a gas turbine according to a fourth aspect of the presentinvention employs the gas turbine blades of any one of the first tothird aspects described above. Accordingly, turbine blade strength andrigidity are ensured, and thus, reliability is enhanced.

Finally, a manufacturing method of gas turbine blades according to afifth aspect of the present invention, in the case of forming thecooling channels in the gas turbine blade of any one of the first tothird aspects described above, includes a base-side elongated holeforming step of forming the base-side elongated holes from a base sideof the turbine blade by electromachining, a communicating hollow portionforming step of forming the communicating hollow portions by decreasingor halting the machining speed of the electromachining at terminal endpositions of the base-side elongated holes, and a tip-side elongatedhole forming step of forming the tip-side elongated holes from tip sideof the turbine blade to make the tip-side elongated holes penetrate intothe communicating hollow portions.

With this manufacturing method, by lowering the machining speed of orhalting the electromachining at the terminal end positions of thebase-side elongated holes, it is possible to easily form thecommunicating hollow portions having larger cross-sectional areas thanthe channel cross-sectional areas of the base-side elongated holes, thusconsequently making it possible to simplify the formation of the coolingchannels as a whole.

Advantageous Effects of Invention

As described above, the gas turbine blades and the manufacturing methodtherefor according to the present invention are capable of simplifyingthe formation of cooling channels provided inside the turbine bladeswhile simultaneously being capable of avoiding a loss of turbine bladestrength and rigidity due to the formation of the cooling channels,thereby increasing reliability of the turbine blades and, consequently,the gas turbine as a whole.

BRIEF DESCRIPTION OF DRAWINGS

FIG. 1 is an overall configuration diagram showing an example of a gasturbine to which turbine blades according to embodiments of the presentinvention are applied.

FIG. 2 is a longitudinal cross-sectional view of the turbine bladesshowing a first embodiment of the present invention.

FIG. 3 is a lateral cross-sectional view of the turbine blades takenalong the line III-III in FIG. 2.

FIG. 4 is a lateral cross-sectional view of the blade portions showingan example in which inner diameters of tip-side elongated holes arealtered in accordance with the plate thickness of the blade portions.

FIG. 5 is a longitudinal cross-sectional view showing the vicinity ofcommunicating hollow portions of cooling channels, where the portion Vin FIG. 2 is enlarged.

FIG. 6 is a longitudinal cross-sectional view of the vicinity ofcommunicating hollow portions of cooling channels, showing an example inwhich inner diameters of base-side elongated holes and the tip-sideelongated holes are made identical.

FIG. 7A is a longitudinal cross-sectional view showing a base-sideelongated hole forming step in a manufacturing procedure of the turbineblades.

FIG. 7B is a longitudinal cross-sectional view showing a communicatinghollow portion forming step in the manufacturing procedure of theturbine blades.

FIG. 7C is a longitudinal cross-sectional view showing a tip-sideelongated hole forming step in the manufacturing procedure of theturbine blades.

FIG. 7D is a longitudinal cross-sectional view showing a state in whichcooling channels are completed in the manufacturing procedure of theturbine blades.

FIG. 8 is a longitudinal cross-sectional view of the turbine bladesshowing a second embodiment of the present invention.

FIG. 9 is a longitudinal cross-sectional view of the turbine bladesshowing a third embodiment of the present invention.

FIG. 10 is a longitudinal cross-sectional view of the turbine bladesshowing a fourth embodiment of the present invention.

DESCRIPTION OF EMBODIMENTS

A plurality of embodiments of gas turbine blades according to thepresent invention will be described below with reference to thedrawings.

First Embodiment

FIGS. 1 to 6 show a first embodiment of the present invention. FIG. 1 isan overall configuration diagram showing an example of a gas turbine towhich turbine blades according to the present invention are applied. Thegas turbine 1 is provided with a compressor 2, a combustor 3, and aturbine 4. The compressor 2 compresses the air taken in from anair-intake port to generate compressed air. The combustor 3 generateshigh-temperature, high-pressure combustion gas by spraying fuel into thecompressed air. The turbine 4 generates a driving force by convertingthe thermal energy of the combustion gas into the rotational energy of arotor 5. Then, the driving fore is transmitted to a generator (notshown) or the like connected to the rotor 5. The turbine 4 is disposedinside a turbine housing 6 which is provided so as to connect with thecombustor 3.

The turbine 4 includes several stages of turbine blades 41 that aredisposed in the rotor 5 so as to integrally rotate therewith, andseveral stages of turbine vanes 42 that are disposed alternately betweenthe individual turbine blades 41 while being secured onto an innercircumferential surface of the turbine housing 6. Then, thehigh-temperature, high-pressure combustion gas generated at thecombustor 3 passes through between these turbine blades 41 and turbinevanes 42 while expanding, thereby rotating the rotor 5 together with theturbine blades 41 to generate the driving force. In this turbine 4, partof the compressed air is extracted from the compressor 2 as cooling air,and members exposed to high-temperature gas, such as the turbine blades41, the turbine vanes 42, and so forth, are, as described below, cooledfrom inside by the cooling air.

In the turbine blades 41, base portions 411, blade portions 412, andplatform portions 413 are integrally formed with durable steel materialhaving heat resistant and corrosion resistant; the base portions 411 arefitted to the rotor 5, the blade portions 412 extend in radialdirections from the rotor 5, and tip portions of the individual bladeportions 412 are circumferentially connected by a ring-shaped shroud415. The platform portions 413 form a continuous cylindrical shape whenindividual turbine blades 41 are attached to the rotor 5, and thus, theflow of the combustion gas is rectified.

A plurality of multi-hole cooling channels 410 are formed inside theturbine blades 41, and the compressed air extracted from the compressor2 is supplied to these cooling channels 410 as the cooling air via flowpaths (not shown) provided inside the rotor 5. The cooling air issupplied from bottom portions of the base portions of the turbine blades41, cools the inside of the turbine blades 41 in the process of flowingin the cooling channels 410 toward the tip portions thereof, and thus,the blade portions 412 are protected from the heat due to thehigh-temperature combustion gas.

The cooling channels 410 are configured having a plurality of straightchannel-like base-side elongated holes 410 a that are formed so as toextend in the longitudinal direction at the base side of the turbineblades 41, a plurality of tip-side elongated holes 410 b that aresimilarly formed in straight-channel-like forms so as to extend in thelongitudinal direction at the tip side of the turbine blades 41, and aplurality of communicating hollow portions 410 c that are interposed atconnecting portions between the base-side elongated holes 410 a and thetip-side elongated holes 410 b to individually allow the two types ofelongated holes 410 a and 410 b to communicate with each other.

As shown in FIG. 3, the tip-side elongated holes 410 b are disposed atnearly equal intervals along curved shapes of the blade portions 412. Asshown in FIG. 4, inner diameters of the tip-side elongated holes 410 bmay be altered in accordance with the plate thickness of the bladeportions 412. Here, the inner diameters of the tip-side elongated holes410 b that pass through portions where the plate thickness of the bladeportions 412 is large are made larger than the inner diameters of thetip-side elongated holes 410 b that pass through portions where theplate thickness is small.

As shown in an enlarged view in FIG. 5, the channel cross-sectionalareas (inner diameters d1) of the base-side elongated holes 410 a arelarger than the channel cross-sectional areas (inner diameters d2) ofthe tip-side elongated holes 410 b. Note that, as shown in FIG. 6, theinner diameters d1 of the base-side elongated holes 410 a and the innerdiameters d2 of the tip-side elongated holes 410 b may be of the samesize. As shown in FIG. 4, when altering the inner diameters of thetip-side elongated holes 410 b in accordance with the plate thickness ofthe blade portions 412, the inner diameters of the base-side elongatedholes 410 a may be similarly altered.

The communicating hollow portions 410 c are formed in spherical shapes,spheroid shapes, or the like, having larger lateral cross-sectionalareas than the channel cross-sectional areas of the base-side elongatedholes 410 a and the tip-side elongated holes 410 b. The communicatinghollow portions 410 c are formed so as to match the positions (height)of the platform portions 413 whose plate thickness is larger than thebase portions 411 and the blade portions 412.

Next, a method of forming the cooling channels 410 in the turbine blades41 configured as above will be described with reference to FIGS. 7A to7D.

First, in a base-side elongated hole forming step shown in FIG. 7A, thebase-side elongated holes 410 a are formed from the base side of theturbine blades 41, that is, the base portions 411 side thereof, byelectromachining, for example, electrical discharge machining,electrochemical machining (preferably nitric-acid electrochemicalmachining), or the like.

Next, in a communicating hollow portion forming step shown in FIG. 7B,the machining speed of the electromachining is lowered or halted to betemporarily maintained at terminal end positions of the base-sideelongated holes 410 a, that is, the vicinity of the height where theplatform portions 413 are formed. Accordingly, the inner diameters ofthe base-side elongated holes 410 a at the terminal end portions areexpanded, thereby forming spherically shaped or spheroid shapedcommunicating hollow portions 410 c inside the platform portions 413.Here, machining of the turbine blades 41 from the base side thereof iscompleted. Note that, the terminal end positions of the base-sideelongated holes 410 a are not limited to the platform portions 413 andmay be provided at the base portions 411.

Next, in a tip-side elongated hole forming step shown in FIG. 7C, thetip-side elongated holes 410 b are formed from the tip side of theturbine blades 41 by electromachining, for example, the electricaldischarge machining or the electrochemical machining, or by milling witha drill or the like, and the machining is completed by having thetip-side elongated holes 410 b penetrate into the communicating hollowportions 410 c.

As shown in FIG. 7D, the base-side elongated holes 410 a, the tip-sideelongated holes 410 b, and the communicating hollow portions 410 c aremade to communicate with each other in this way, thus completing thecooling channels 410.

In this way, by employing the machining method in which the machiningspeed of the electromachining is lowered or halted at the terminal endpositions of the base-side elongated holes 410 a, the communicatinghollow portions 410 c having larger cross-sectional areas than thechannel cross-sectional areas of the base-side elongated holes 410 a caneasily be formed, the ease of penetration by the tip-side elongatedholes 410 b that lead thereto is enhanced, thus consequently making itpossible to simplify formation of the cooling channels 410 as a whole.

In the turbine blades 41 configured as above, the cooling channels 410are configured having the plurality of the base-side elongated holes 410a that extend in the longitudinal direction at the base side of theturbine blades 41, the plurality of the tip-side elongated holes 410 bthat extend in the longitudinal direction at the tip side of the turbineblades 41, and the communicating hollow portions 410 c that arepositioned at the connecting portions of the individual elongated holes410 a and 410 b; and the cross-sectional areas (inner diameters d3) ofthe communicating hollow portions 410 c are larger than the channelcross-sectional areas (inner diameters d1 and d2) of the individualelongated holes 410 a and 410 b; therefore, even if the positions of thetip-side elongated holes 410 b are slightly shifted in the tip-sideelongated hole forming step shown in FIG. 7C, the level of penetrationinto the communicating hollow portions 410 c is much improved, thusmaking it possible to simplify formation of the cooling channels 410.

In addition, because the base-side elongated holes 410 a are formed inthe plurality of straight-channel-like forms instead of a single hollowportion, sufficient effective cross-sectional areas are ensured at theseportions of the turbine blades 41, and there is no loss of strength andrigidity of the turbine blades 41. Moreover, because the communicatinghollow portions 410 c where the lateral cross-sectional areas is thelargest in the cooling channels 410 are formed inside the platformportions 413 where the plate thickness is the largest in the turbineblades 41, the portions where the effective cross-sectional areas of theturbine blades 41 become small in practice are minimized, thereby makingit possible to reliably reduce the reduction in strength and rigidity ofthe turbine blades 41.

Note that, although machining is started from the base side toward thetip side in the elongated hole forming steps show in FIGS. 7A to 7C, incontrast, machining may be started from the tip side toward the baseside.

Finally, by applying the turbine blades 41 whose strength and rigidityare ensured in this way to the turbine 4, it is possible to considerablyenhance the reliability of the gas turbine 1.

Second Embodiment

Next, a second embodiment of the present invention will be describedwith reference to FIG. 8. Except for the point that the positions in thelongitudinal direction differ for the plurality of the communicatinghollow portions 410 c that constitute the cooling channels 410, turbineblades 51 illustrated in this second embodiment are similar to theturbine blades 41 of the first embodiment shown in FIG. 2.

Here, the communicating hollow portions 410 c are disposed, for example,in a staggered manner by varying the heights thereof in the verticaldirection, so that the heights of the communicating hollow portions 410c that are adjacent to each other among the plurality of thecommunicating hollow portions 410 c differ. Even if the heights arealtered in this way, it is desirable that all of the communicatinghollow portions 410 c be formed so as to be positioned inside theplatform portions 413.

With this configuration, the communicating hollow portions 410 c thatare adjacent to each other are not arranged at the same height, anddistances between the individual communicating hollow portions 410 c areincreased; therefore, a reduction of the effective cross-sectional areasof the turbine blades 51 at the positions of the communicating hollowportions 410 c is avoided, thereby more effectively preventing the lossof strength and rigidity of the turbine blades 51.

Third Embodiment

Next, a third embodiment of the present invention will be described withreference to FIG. 9. Except for the point that lengths from tip ends ofa plurality of tip-side elongated holes 610 b to the communicatinghollow portions are set to be the same, turbine blades 61 illustrated inthis third embodiment are similar to the turbine blades 41 of the firstembodiment shown in FIG. 2.

By setting the lengths of the plurality of the tip-side elongated holes610 b to be the same, simultaneous machining with a plurality ofelectrodes or drills is possible, variance in the accuracy of machiningof the elongated holes does not occur, and the accuracy of machining ismuch improved.

Fourth Embodiment

Next, a fourth embodiment of the present invention will be describedwith reference to FIG. 10. Except for the point that lengths from tipends of a plurality of tip-side elongated holes 710 b to thecommunicating hollow portions are set to be the same, and furthermorelengths from end faces of base portions 411 of a plurality of base-sideelongated holes 710 a to the communicating hollow portions are also setto be the same, turbine blades 71 illustrated in this fourth embodimentare similar to the turbine blades 41 of the first embodiment shown inFIG. 2.

By setting the lengths of the tip-side elongated holes 710 b and thelengths of the base-side elongated holes 710 a respectively to be thesame, similar effects to those of the turbine blade 61 in the thirdembodiment can be obtained.

REFERENCE SIGNS LIST

-   1 gas turbine-   2 compressor-   3 combustor-   4 turbine-   5 rotor-   6 turbine housing-   41 turbine blade-   51 turbine blade-   61 turbine blade-   71 turbine blade-   410 cooling channel-   410 a base-side elongated hole-   410 b tip-side elongated hole-   410 c communicating hollow portion-   411 base portion-   412 blade portion-   413 platform portion-   415 shroud

The invention claimed is:
 1. A gas turbine blade in which coolingchannels are formed inside the turbine blade, and the turbine blade iscooled by causing cooling air to circulate through the cooling channels,wherein the cooling channels comprise: a plurality of straightchannel-like base-side elongated holes that extend in a longitudinaldirection at a base side of the turbine blade, a plurality of straightchannel-like tip-side elongated holes that extend in a longitudinaldirection at a tip side of the turbine blade, and a plurality ofcommunicating hollow portions that are interposed at connection portionsbetween the base-side elongated holes and the tip-side elongated holesto individually allow the two types of elongated holes to communicatewith each other, and that have larger cross-sectional areas than thechannel cross-sectional areas of the two types of elongated holes,wherein the communicating hollow portions are formed so as to match theposition of a platform portion of the turbine blade, and wherein, amongthe plurality of the communicating hollow portions, the communicatinghollow portions that are adjacent to each other are set at differentheights.
 2. A gas turbine blade according to claim 1, wherein at leastlengths from tip ends of the plurality of the tip-side elongated holesto the communicating hollow portions are set to be the same.
 3. A gasturbine employing the gas turbine blade according to claim 1 in aturbine.
 4. A manufacturing method of a gas turbine blade, in the caseof forming the cooling channels in the gas turbine blade according toclaim 1, comprising: a base-side elongated hole forming step of formingthe base-side elongated holes from a base side of the turbine blade byelectromachining, a communicating hollow portion forming step of formingthe communicating hollow portions by decreasing or halting the machiningspeed of the electromachining at terminal end positions of the base-sideelongated holes, and a tip-side elongated hole forming step of formingthe tip-side elongated holes from tip side of the turbine blade to makethe tip-side elongated holes penetrate into the communicating hollowportions.